CN110901126B - A kind of full-cured aramid honeycomb-assisted shaping process method - Google Patents

A kind of full-cured aramid honeycomb-assisted shaping process method Download PDF

Info

Publication number
CN110901126B
CN110901126B CN201911234377.2A CN201911234377A CN110901126B CN 110901126 B CN110901126 B CN 110901126B CN 201911234377 A CN201911234377 A CN 201911234377A CN 110901126 B CN110901126 B CN 110901126B
Authority
CN
China
Prior art keywords
honeycomb
curing
configuration
fully
cured
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201911234377.2A
Other languages
Chinese (zh)
Other versions
CN110901126A (en
Inventor
易文清
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
CETC 54 Research Institute
Original Assignee
CETC 54 Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by CETC 54 Research Institute filed Critical CETC 54 Research Institute
Priority to CN201911234377.2A priority Critical patent/CN110901126B/en
Publication of CN110901126A publication Critical patent/CN110901126A/en
Application granted granted Critical
Publication of CN110901126B publication Critical patent/CN110901126B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0089—Producing honeycomb structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/34—Electrical apparatus, e.g. sparking plugs or parts thereof
    • B29L2031/3456—Antennas, e.g. radomes

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

The invention discloses a process method for auxiliary shaping of a fully-cured aramid fiber honeycomb. The method is simple to operate and low in cost, realizes the large-range application of the fully-cured aramid honeycomb on products with large curvature and double curvature, adopts a glue spraying method to carry out auxiliary setting on the fully-cured aramid honeycomb, realizes temporary secondary setting on the fully-cured aramid honeycomb, and facilitates the operation of workers. The purpose of applying the fully-cured aramid fiber honeycomb to products with double curvature and large curvature is really realized.

Description

Auxiliary shaping process method for fully-cured aramid fiber honeycomb
Technical Field
The invention belongs to the field of antenna skin preparation processes, and relates to a process method for auxiliary shaping of a fully-cured aramid fiber honeycomb.
Background
At present, aramid fiber honeycombs have unique electrical properties, mechanical properties and extremely high dimensional stability, and therefore have wide application in the aspects of airborne, shipborne and spaceborne radars, radar antenna feed source functional structural members, light antenna support structures, overhead antenna guys and the like. The aramid fiber honeycomb mainly has two types, one type is a semi-cured prepreg paper honeycomb, the other type is a fully-cured honeycomb, glue in the semi-cured honeycomb is in a semi-cured state, and the aramid fiber honeycomb can be cured and shaped for the second time during heating. The cost is high, the product needs to be stored in a cold storage, and the storage period is only 15 days. The risk of overdue materials is high. And the semi-cured honeycomb is provided with less and less quantity in the market at present, and the purchase channel is difficult. The glue in the honeycomb is completely cured, and the fully cured honeycomb can be stored at room temperature for a long time. But the secondary molding effect is inferior compared to the semi-cured honeycomb. Particularly, when the honeycomb height is high and honeycomb sandwich products with large curvature and double curvature are produced, the resilience force of the fully cured honeycomb is large, the operation of workers is difficult, and the honeycomb sandwich products cannot be effectively shaped.
Disclosure of Invention
In order to solve the problem that the fully-cured honeycomb is difficult to prepare a double-curvature configuration according to a required shape, the invention provides an effective auxiliary method for shaping the fully-cured honeycomb. Therefore, the full-cured honeycomb can be widely applied to products with double curvature and large curvature.
The technical scheme adopted by the invention is as follows:
a process method for auxiliary shaping of fully-cured aramid fiber honeycomb is characterized by comprising the following steps:
s1, preparing a mold, presetting a semicircular configuration with curvature, and forming a required configuration groove on the surface of the mold, wherein the surface shape of the configuration groove is consistent with the semicircular configuration;
s2, preparing a front skin, paving a composite material prepreg in the configuration groove, and performing hot pressing by using an autoclave after the paving is finished to obtain the front skin;
s3, preparing a sandwich, cutting the fully-cured honeycomb, just completely embedding the cut honeycomb into the configuration groove, enabling the bottom surface of the honeycomb to be conformal with the surface of the configuration groove, spraying structural adhesive on the concave surface of the fully-cured honeycomb, and enabling the structural adhesive to form a structural adhesive layer on the concave surface of the fully-cured honeycomb to obtain a mold with the sandwich;
s4, vacuum packaging, namely placing the mould provided with the sandwich in the step S3 into a vacuum bag for vacuumizing, and curing for 24 hours at the curing temperature of 15-40 degrees;
s5, preparing a rear skin, paving a composite material prepreg in the configuration groove, and performing hot pressing by using an autoclave after the paving is finished to obtain the rear skin;
s6, assembling, namely sequentially stacking a front skin, a sandwich and a rear skin from bottom to top and placing the front skin, the sandwich and the rear skin into the configuration groove, and placing epoxy resin adhesive films between the front skin and the sandwich and between the sandwich and the rear skin;
and S7, curing and forming, namely putting the whole into a vacuum tank, and curing and forming at 130 ℃ under vacuum negative pressure to obtain the hemispherical cavity shell.
Further, in the step S3, in the sandwich preparation process, vertical pressure is always provided for the surface of the fully-cured honeycomb in the structural adhesive spraying process, and the fully-cured honeycomb is continuously pressed into the configuration groove.
Further, S4, in the vacuum packaging process, vertical pressure is always provided for the surface of the fully-cured honeycomb in the vacuumizing process, and the fully-cured honeycomb is continuously pressed into the configuration groove until the curing is finished.
Further, in step S7, a teflon release cloth is first laid on the inner surface of the configuration groove.
Compared with the prior art, the invention has the following beneficial effects: 1. compared with semi-solidified aramid fiber honeycombs, the semi-solidified honeycombs need to be stored in a refrigeration house, and the quality guarantee period is about 15 days. The fully cured honeycomb can be stored at room temperature for a long time. The shaping process ensures the use of the fully-cured honeycomb, reduces the risk of honeycomb deterioration and greatly reduces the storage cost.
2. The full-curing honeycomb replaces the semi-curing honeycomb, so that the operation process is better, and meanwhile, the full-curing honeycomb is more environment-friendly than the semi-curing honeycomb.
3. When the product with double curvature and large curvature is manufactured, 3M glue spraying auxiliary shaping is adopted to control the resilience force of the fully cured honeycomb. The temporary shaping is ensured, and the smooth paving and pasting operation of workers is ensured. The application of the fully cured honeycomb on double-curvature products is fundamentally ensured.
4. And (3) setting the fully-cured honeycomb by using a glue spraying method, compared with a baking oven heating method, setting the semi-cured honeycomb. The glue spraying method does not need heating, and the preparation cost is reduced.
Drawings
FIG. 1 is a schematic diagram of preparation of a fully-cured aramid fiber honeycomb sandwich.
In the figure, a mould 1, a front skin 2, an epoxy film 3, a full-curing honeycomb 4, a film 5 and a rear skin 6.
Detailed Description
The present invention will be further described with reference to FIG. 1.
A process method for auxiliary shaping of fully-cured aramid fiber honeycomb comprises the following steps:
s1, preparing a mold, presetting a semicircular configuration with curvature, and forming a required configuration groove on the surface of the mold, wherein the surface shape of the configuration groove is consistent with the semicircular configuration;
s2, preparing a front skin, paving a composite material prepreg in the configuration groove, and performing hot pressing by using an autoclave after the paving is finished to obtain the front skin;
s3, preparing a sandwich, cutting the fully-cured honeycomb, enabling the cut honeycomb to be just completely embedded into the configuration groove, always providing vertical pressure on the surface of the fully-cured honeycomb, continuously pressing the fully-cured honeycomb into the configuration groove, enabling the bottom surface of the honeycomb to be conformal to the surface of the configuration groove, spraying structural adhesive on the concave surface of the fully-cured honeycomb, and enabling the structural adhesive to form a structural adhesive layer on the concave surface of the fully-cured honeycomb to obtain a mold matched with the sandwich;
s4, vacuum packaging, namely placing the die provided with the sandwich core in the step S3 into a vacuum bag, vacuumizing, maintaining the pressure at 0.02Mpa, curing for 24 hours at the curing temperature of 15-40 degrees, always providing vertical pressure on the surface of the fully-cured honeycomb in the whole process, continuously pressing the fully-cured honeycomb into a configuration groove until the curing is finished, wiping the outer surface of the fully-cured honeycomb by using ethanol or acetone after the curing is finished, and removing glue spraying residues on the surface of the honeycomb;
s5, preparing a rear skin, paving a composite material prepreg in the configuration groove, and performing hot pressing by using an autoclave after the paving is finished to obtain the rear skin;
s6, assembling, namely sequentially stacking a front skin, a sandwich and a rear skin from bottom to top and placing the front skin, the sandwich and the rear skin into the configuration groove, and placing epoxy resin adhesive films between the front skin and the sandwich and between the sandwich and the rear skin;
s7, curing and forming, namely paving Teflon demolding cloth on the inner surface of the configuration groove, putting the whole into a vacuum tank, and curing and forming at 130 ℃ under vacuum negative pressure to obtain a hemispherical cavity shell;
and S8, demolding, namely demolding the double-curvature product after the curing is completed.
S9, shape modification and paint spraying, polishing the rubber bumps on the surface, and repairing the surface defects. And removing the release agent. And then carrying out three-proofing treatment of spray painting. Obtaining the honeycomb sandwich product.

Claims (2)

1.一种全固化芳纶蜂窝辅助定型的工艺方法，其特征在于包括步骤：1. a process method for full-curing aramid honeycomb assisted shaping, is characterized in that comprising the steps: S1.制备模具，预设具备曲率的半圆状构型，在模具表面开设所需的构型凹槽，构型凹槽表面形状与所述的半圆状构型一致；S1. prepare a mold, preset a semicircular configuration with curvature, and set a required configuration groove on the surface of the mold, and the surface shape of the configuration groove is consistent with the semicircular configuration; S2.制备前蒙皮，在所述构型凹槽内铺覆复合材料预浸料，铺覆完毕后采用热压罐进行热压，得到前蒙皮；S2. Prepare the front skin, lay the composite material prepreg in the configuration groove, and use an autoclave for hot pressing after the coating is completed to obtain the front skin; S3.制备夹芯，对全固化蜂窝进行裁切，裁切完毕后的蜂窝刚好完全嵌合至所述的构型凹槽内，蜂窝底面与构型凹槽表面共形，对全固化蜂窝凹面喷涂结构胶，结构胶在全固化蜂窝的凹面形成结构胶层，得到配装有夹芯的模具；制备夹芯过程中，喷涂结构胶过程中对全固化蜂窝表面始终提供垂直压力，全固化蜂窝持续压入在构型凹槽中；S3. Prepare the sandwich, cut the fully cured honeycomb, the cut honeycomb is just completely fitted into the configuration groove, the bottom surface of the honeycomb is conformal to the surface of the configuration groove, and the concave surface of the fully cured honeycomb is Structural adhesive is sprayed, and the structural adhesive forms a structural adhesive layer on the concave surface of the fully cured honeycomb to obtain a mold equipped with a core; in the process of preparing the core, vertical pressure is always provided on the surface of the fully cured honeycomb during the process of spraying the structural adhesive, and the fully cured honeycomb Continuously pressed into the configuration groove; S4.真空封装，对步骤S3中的配装有夹芯的模具置入真空袋内抽真空，固化24小时，固化温度为15°-40°；真空封装过程中，抽真空过程中对全固化蜂窝表面始终提供垂直压力，全固化蜂窝持续压入在构型凹槽，直至固化结束；S4. vacuum encapsulation, placing the mold equipped with the core in step S3 into a vacuum bag and vacuuming, curing for 24 hours, and the curing temperature being 15°-40°; during the vacuum encapsulation process, the full curing The honeycomb surface always provides vertical pressure, and the fully cured honeycomb continues to be pressed into the configuration groove until the end of curing; S5.制备后蒙皮，在所述构型凹槽内铺覆复合材料预浸料，铺覆完毕后采用热压罐进行热压，得到后蒙皮；S5. The back skin is prepared, and the composite material prepreg is covered in the configuration groove, and after the covering is completed, an autoclave is used for hot pressing to obtain the back skin; S6.组装，将前蒙皮，夹芯，后蒙皮按照由下至上依次层叠的置入构型凹槽内，位于前蒙皮与夹芯之间和夹芯与后蒙皮之间皆置入环氧树脂胶膜；S6. Assemble, put the front skin, the core and the back skin into the configuration grooves in a sequence from bottom to top, between the front skin and the core and between the core and the back skin into epoxy resin film; S7. 固化成型，将整体置入真空罐中，真空负压下在130℃固化成型，得到半球形空腔壳体。S7. Curing and molding, placing the whole in a vacuum tank, curing and molding at 130°C under vacuum negative pressure to obtain a hemispherical cavity shell. 2.根据权利要求1所述的一种全固化芳纶蜂窝辅助定型的工艺方法，其特征在于，步骤S6 中，首先对构型凹槽内面铺覆铁氟龙脱模布。2 . The process method for fully cured aramid honeycomb assisted shaping according to claim 1 , wherein, in step S6 , firstly, the inner surface of the shaped groove is covered with Teflon release cloth. 3 .
CN201911234377.2A 2019-12-05 2019-12-05 A kind of full-cured aramid honeycomb-assisted shaping process method Active CN110901126B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911234377.2A CN110901126B (en) 2019-12-05 2019-12-05 A kind of full-cured aramid honeycomb-assisted shaping process method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911234377.2A CN110901126B (en) 2019-12-05 2019-12-05 A kind of full-cured aramid honeycomb-assisted shaping process method

Publications (2)

Publication Number Publication Date
CN110901126A CN110901126A (en) 2020-03-24
CN110901126B true CN110901126B (en) 2021-08-31

Family

ID=69822816

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911234377.2A Active CN110901126B (en) 2019-12-05 2019-12-05 A kind of full-cured aramid honeycomb-assisted shaping process method

Country Status (1)

Country Link
CN (1) CN110901126B (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111730879A (en) * 2020-06-28 2020-10-02 苏州芳磊蜂窝复合材料有限公司 Method for manufacturing large-curved-surface aramid paper honeycomb cylinder
CN114055807B (en) * 2021-11-12 2024-05-24 广东汇天航空航天科技有限公司 Method for forming composite material part, formed part and aircraft
CN116160701A (en) * 2022-12-09 2023-05-26 上海复合材料科技有限公司 Forming method of large-curvature co-cured glass fiber reinforced plastic skin aramid fiber paper honeycomb sandwich structure

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104553238A (en) * 2014-12-12 2015-04-29 中航复合材料有限责任公司 Method for reinforcing surface stability of core of honeycomb-like porous structure by hot film blowing and breaking method
CN109291486A (en) * 2018-08-23 2019-02-01 江苏恒神股份有限公司 A kind of hyperbolicity Special paper honeycomb structure setting process method
CN109367068A (en) * 2018-10-16 2019-02-22 上海船舶工艺研究所(中国船舶工业集团公司第十研究所) A kind of carbon fiber material ship shell and its manufacturing method

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104553238A (en) * 2014-12-12 2015-04-29 中航复合材料有限责任公司 Method for reinforcing surface stability of core of honeycomb-like porous structure by hot film blowing and breaking method
CN109291486A (en) * 2018-08-23 2019-02-01 江苏恒神股份有限公司 A kind of hyperbolicity Special paper honeycomb structure setting process method
CN109367068A (en) * 2018-10-16 2019-02-22 上海船舶工艺研究所(中国船舶工业集团公司第十研究所) A kind of carbon fiber material ship shell and its manufacturing method

Also Published As

Publication number Publication date
CN110901126A (en) 2020-03-24

Similar Documents

Publication Publication Date Title
CN110481059B (en) A composite foam sandwich structure and its forming method
CN110901126B (en) A kind of full-cured aramid honeycomb-assisted shaping process method
CN103909658B (en) Composite material connecting skirt forming method and mold and inner rubber core mold forming mold
CN115464899B (en) A composite material forming method for a hollow rotating body structure with front and rear ends
CN108891040B (en) A kind of manufacturing method of composite material horizontal tail for small and medium-sized unmanned aerial vehicle
CN103407170B (en) A kind of preparation method of satellite antenna reflecting surface
CN108790210A (en) Composite material air intake duct and preparation method thereof and aircraft
CN115847865A (en) Autoclave molding method of variable-curvature variable-section omega-shaped composite material pipeline piece
CN110193956A (en) A kind of small drone composite material vertical tail moulding technique
CN110774623A (en) Manufacturing method of simple-modeling carbon fiber composite part of hydrogen energy automobile
CN112936909A (en) Forming process of thickened V-shaped composite material part at bottom of trainer
CN109203516A (en) A kind of manufacturing method of wind electricity blade
CN109367071B (en) Production method of fiber reinforced composite ejection push arm
CN115107296A (en) Die and method for integrally forming head conical part with smooth inner and outer surfaces
CN115816859B (en) Low-leakage-rate process forming method for glass fiber reinforced resin matrix composite material sealed box
CN117359969A (en) A foam sandwich composite material structure and its forming method
CN115302815A (en) Manufacturing method of special-shaped airplane frame upright post
CN115709583A (en) Forming method of seal head assembly and engine shell
CN106393733A (en) Manufacturing method of solid wall composite material radar cover
CN113370550B (en) Composite sandwich spherical crown structure and forming method thereof
CN112721234B (en) High-precision composite material antenna reflecting surface skin forming method
CN114122709A (en) Manufacturing method of conformal radome
CN112046036B (en) Method for manufacturing composite material ejection support arm
CN106273535A (en) A kind of forming method of semiclosed composite structure
CN113942253B (en) Method for integrally preparing composite shelter

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant